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GOE 462 AIRFOIL (goe462-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 462 AIRFOIL (goe462-il)
Reynolds number: 1,000,000
Max Cl/Cd: 107.34 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe462-il-1000000.txt
Download as CSV file: xf-goe462-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 462 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.1460   0.10934   0.10655  -0.0852   0.7086   0.0096
 -10.500   0.1541   0.10705   0.10415  -0.0860   0.6811   0.0097
 -10.000   0.1703   0.10214   0.09905  -0.0874   0.6353   0.0098
  -9.750   0.1804   0.10005   0.09686  -0.0878   0.6147   0.0099
  -9.500   0.1910   0.09829   0.09501  -0.0882   0.5948   0.0101
  -9.250   0.2022   0.09659   0.09326  -0.0887   0.5820   0.0104
  -9.000   0.2125   0.09461   0.09123  -0.0894   0.5693   0.0105
  -8.750   0.2231   0.09270   0.08928  -0.0900   0.5579   0.0112
  -8.500   0.2332   0.09071   0.08725  -0.0907   0.5488   0.0115
  -8.250   0.2415   0.08815   0.08468  -0.0917   0.5421   0.0126
  -8.000   0.2501   0.08603   0.08254  -0.0924   0.5344   0.0127
  -7.750   0.2590   0.08406   0.08056  -0.0930   0.5280   0.0127
  -7.500   0.2660   0.08146   0.07796  -0.0933   0.5220   0.0129
  -7.250   0.2767   0.07983   0.07629  -0.0932   0.5138   0.0131
  -7.000   0.2867   0.07831   0.07477  -0.0932   0.5078   0.0132
  -6.750   0.2953   0.07693   0.07337  -0.0929   0.5013   0.0135
  -6.500   0.3064   0.07529   0.07172  -0.0935   0.4957   0.0138
  -6.250   0.3193   0.07347   0.06990  -0.0945   0.4901   0.0142
  -6.000   0.3325   0.07156   0.06797  -0.0957   0.4843   0.0147
  -5.750   0.3472   0.06879   0.06519  -0.0988   0.4796   0.0161
  -5.500   0.3639   0.06635   0.06275  -0.1015   0.4744   0.0162
  -5.250   0.3788   0.06331   0.05969  -0.1038   0.4689   0.0165
  -5.000   0.3963   0.06179   0.05814  -0.1047   0.4625   0.0168
  -4.750   0.4150   0.06063   0.05696  -0.1056   0.4549   0.0175
  -4.500   0.4350   0.05883   0.05510  -0.1077   0.4480   0.0182
  -4.000   0.4899   0.05309   0.04929  -0.1175   0.4349   0.0205
  -3.750   0.5180   0.05012   0.04628  -0.1219   0.4286   0.0205
  -3.250   0.6947   0.02586   0.02134  -0.1751   0.4153   0.0266
  -3.000   0.7209   0.02587   0.02134  -0.1749   0.4066   0.0278
  -2.750   0.7674   0.02319   0.01843  -0.1818   0.3973   0.0301
  -2.500   0.8123   0.02073   0.01568  -0.1878   0.3874   0.0316
  -2.250   0.8501   0.01936   0.01410  -0.1911   0.3789   0.0337
  -2.000   0.8814   0.01882   0.01345  -0.1923   0.3705   0.0355
  -1.750   0.9130   0.01821   0.01274  -0.1936   0.3638   0.0371
  -1.500   0.9450   0.01754   0.01193  -0.1949   0.3570   0.0388
  -1.250   0.9746   0.01723   0.01152  -0.1955   0.3509   0.0403
  -1.000   1.0030   0.01717   0.01143  -0.1955   0.3458   0.0440
  -0.750   1.0342   0.01662   0.01078  -0.1966   0.3401   0.0487
  -0.500   1.0633   0.01638   0.01064  -0.1970   0.3350   0.0736
  -0.250   1.0909   0.01631   0.01054  -0.1970   0.3311   0.0825
   0.000   1.1142   0.01688   0.01112  -0.1956   0.3270   0.0834
   0.250   1.1378   0.01734   0.01157  -0.1946   0.3225   0.0842
   0.500   1.1626   0.01764   0.01186  -0.1938   0.3194   0.0854
   0.750   1.1975   0.01663   0.01071  -0.1958   0.3167   0.0925
   1.000   1.2217   0.01702   0.01110  -0.1950   0.3136   0.0931
   1.250   1.2462   0.01733   0.01140  -0.1942   0.3103   0.0938
   1.500   1.2712   0.01755   0.01158  -0.1937   0.3063   0.0948
   1.750   1.2970   0.01764   0.01167  -0.1934   0.3037   0.0960
   2.000   1.3232   0.01772   0.01175  -0.1931   0.3016   0.0989
   2.250   1.3582   0.01685   0.01074  -0.1949   0.2991   0.1043
   2.500   1.3843   0.01690   0.01077  -0.1946   0.2966   0.1050
   2.750   1.4100   0.01698   0.01082  -0.1943   0.2939   0.1059
   3.000   1.4353   0.01710   0.01091  -0.1940   0.2906   0.1072
   3.250   1.4624   0.01706   0.01083  -0.1940   0.2884   0.1094
   3.500   1.4974   0.01620   0.00983  -0.1956   0.2869   0.1149
   3.750   1.5235   0.01625   0.00989  -0.1954   0.2851   0.1157
   4.000   1.5490   0.01635   0.00999  -0.1951   0.2828   0.1164
   4.250   1.5743   0.01645   0.01009  -0.1947   0.2803   0.1175
   4.500   1.5994   0.01658   0.01016  -0.1944   0.2759   0.1190
   4.750   1.6270   0.01650   0.01004  -0.1945   0.2722   0.1228
   5.000   1.6570   0.01614   0.00960  -0.1950   0.2698   0.1263
   5.250   1.6820   0.01625   0.00971  -0.1947   0.2658   0.1270
   5.500   1.7060   0.01646   0.00989  -0.1942   0.2614   0.1278
   5.750   1.7303   0.01661   0.01003  -0.1938   0.2573   0.1290
   6.000   1.7560   0.01665   0.01006  -0.1936   0.2516   0.1307
   6.250   1.7804   0.01683   0.01013  -0.1932   0.2428   0.1341
   6.500   1.8065   0.01683   0.00997  -0.1931   0.2320   0.1374
   6.750   1.8248   0.01746   0.01040  -0.1919   0.2079   0.1382
   7.000   1.8174   0.02014   0.01261  -0.1869   0.1422   0.1420
   7.250   1.7903   0.02348   0.01551  -0.1789   0.0633   0.1421
   7.500   1.7812   0.02518   0.01714  -0.1735   0.0177   0.1429
   7.750   1.7948   0.02575   0.01773  -0.1717   0.0152   0.1435
   8.000   1.8113   0.02616   0.01812  -0.1704   0.0145   0.1404
   8.250   1.8223   0.02694   0.01895  -0.1684   0.0138   0.1410
   8.500   1.8315   0.02789   0.01995  -0.1664   0.0130   0.1419
   8.750   1.8378   0.02913   0.02128  -0.1643   0.0120   0.1431
   9.000   1.8442   0.03048   0.02269  -0.1624   0.0116   0.1456
   9.250   1.8523   0.03178   0.02403  -0.1608   0.0112   0.1469
   9.500   1.8584   0.03334   0.02563  -0.1593   0.0108   0.1476
   9.750   1.8632   0.03513   0.02748  -0.1579   0.0105   0.1485
  10.000   1.8678   0.03704   0.02944  -0.1568   0.0101   0.1494
  10.250   1.8685   0.03944   0.03193  -0.1556   0.0098   0.1499
  10.500   1.8667   0.04227   0.03486  -0.1546   0.0095   0.1503
  10.750   1.8614   0.04568   0.03838  -0.1537   0.0092   0.1507
  11.000   1.8493   0.05019   0.04305  -0.1532   0.0089   0.1509
  11.250   1.8342   0.05542   0.04845  -0.1531   0.0087   0.1512
  11.500   1.8312   0.05920   0.05231  -0.1532   0.0085   0.1516
  11.750   1.8234   0.06381   0.05704  -0.1536   0.0084   0.1520
  12.000   1.8124   0.06906   0.06242  -0.1542   0.0083   0.1524
  12.250   1.7993   0.07483   0.06832  -0.1550   0.0082   0.1528
  12.500   1.7844   0.08100   0.07462  -0.1561   0.0081   0.1532
  12.750   1.7676   0.08765   0.08142  -0.1574   0.0080   0.1535
  13.000   1.7506   0.09450   0.08840  -0.1589   0.0079   0.1540
  13.250   1.7335   0.10151   0.09554  -0.1606   0.0079   0.1544
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